CN219565484U - Unmanned plane - Google Patents

Abstract

The utility model provides an unmanned aerial vehicle, comprising: a storage section; the unmanned aerial vehicle body comprises a fuselage, a plurality of wings and a plurality of elastic components, wherein the plurality of elastic components are connected with the plurality of wings in a one-to-one correspondence manner, the plurality of wings are distributed around the circumference of the fuselage and are hinged with the fuselage, the fuselage and the plurality of wings are inserted in the containing part in a pluggable manner, and the wings have folding positions and unfolding positions relative to the fuselage; in the process of inserting the fuselage into the accommodating part, the accommodating part is abutted with the plurality of wings and drives the plurality of wings to rotate from the unfolding position to the folding position; in the process that the fuselage is pulled out from the storage part, a plurality of elastic components respectively drive corresponding wings to rotate from a folding position to an unfolding position. According to the technical scheme provided by the utility model, the plurality of wings can be folded and unfolded simultaneously in the process of storing and deploying the unmanned aerial vehicle body, so that the operation of storing and deploying the unmanned aerial vehicle body is simplified, and the efficiency of storing and deploying the unmanned aerial vehicle body is improved.

Description

Unmanned plane

Technical Field

The utility model relates to the technical field of unmanned aerial vehicle deployment and storage, in particular to an unmanned aerial vehicle.

Background

At present, unmanned aerial vehicle technology is developed rapidly, and is widely applied to the fields of aerial photography, monitoring and the like, thereby bringing convenience to the work and the life of people. In many application scenarios, it is necessary to rapidly deploy and house the unmanned aerial vehicle, so as to improve the working efficiency. In the prior art, a detachable wing or a folding wing is often adopted, taking a folding wing disclosed by a patent number 202121106704.9 and named as a "folding wing of a flying device" as an example, a folding wing is provided so as to realize rapid deployment and storage of an unmanned aerial vehicle body, but storage and deployment of the unmanned aerial vehicle body still need to respectively fold or unfold a plurality of wings, and storage and deployment efficiency of the unmanned aerial vehicle body are affected.

Disclosure of Invention

The utility model provides an unmanned aerial vehicle, which aims to solve the problem of low storage and deployment efficiency of unmanned aerial vehicle wings in the prior art.

In order to solve the above problems, the present utility model provides a unmanned aerial vehicle comprising: a storage section; the unmanned aerial vehicle body comprises a fuselage, a plurality of wings and a plurality of elastic components, wherein the plurality of elastic components are connected with the plurality of wings in a one-to-one correspondence manner, the plurality of wings are distributed around the circumference of the fuselage and are hinged with the fuselage, the fuselage and the plurality of wings are inserted in the containing part in a pluggable manner, and the wings have folding positions and unfolding positions relative to the fuselage; in the process of inserting the fuselage into the accommodating part, the accommodating part is abutted with the plurality of wings and drives the plurality of wings to rotate from the unfolding position to the folding position; in the process that the fuselage is pulled out from the storage part, a plurality of elastic components respectively drive corresponding wings to rotate from a folding position to an unfolding position.

Further, the rotation direction of the wings is the same as the inserting and pulling direction of the fuselage, and under the condition that the unmanned aerial vehicle body is inserted in the containing part, the wings are all in folding positions, and the extending directions of the wings are parallel to or have included angles with the inserting and pulling direction of the fuselage; under the condition that unmanned aerial vehicle body and storage part separate, fuselage and a plurality of wing all with storage part interval, a plurality of wings all are in the expansion position, a plurality of wings are located the coplanar, and the extending direction of a plurality of wings and the plug direction of fuselage are perpendicular.

Further, the outer peripheral surface of the machine body is provided with a plurality of accommodating grooves corresponding to the elastic components one by one, the extending directions of the accommodating grooves are all parallel to the inserting and pulling directions of the machine body, the elastic components comprise sliding blocks, supporting rods and elastic pieces, the sliding blocks and the elastic pieces are all arranged in the accommodating grooves, the sliding blocks are movably arranged and are abutted to the elastic pieces, one ends of the supporting rods are fixedly connected with the sliding blocks, and the other ends of the supporting rods are hinged to the wings.

Further, the holding tank includes the first cell body and the second cell body of intercommunication each other, and the width of second cell body is greater than the width of first cell body, and first cell body is used for accomodating the bracing piece, and slider and elastic component set up in the second cell body, and slider movably sets up and the roof butt with the second cell body to the rotation scope of restriction wing.

Further, the wing includes horn and paddle subassembly, and the one end of a plurality of horns sets up respectively in a plurality of holding tank extending direction on same one side and articulated with the fuselage, and paddle subassembly includes motor and a plurality of blade, and the motor setting is connected at the other end of horn and with a plurality of blade drive to drive a plurality of blades and rotate.

Further, the wing comprises a plurality of stop blocks, the stop blocks are arranged on one side, deviating from the accommodating groove, of the horn along the extending direction of the accommodating groove, and the stop blocks are matched with the horn stop blocks to limit the rotation range of the horn.

Further, the storage part comprises a box body, the box body is provided with a first storage cavity and a plurality of limit grooves distributed along the circumferential direction of the first storage cavity, the unmanned aerial vehicle body is inserted in the first storage cavity in a pluggable manner, the openings of the limit grooves are respectively abutted with the corresponding wings and drive the wings to rotate from the unfolding position to the folding position in the process of inserting the unmanned aerial vehicle body into the first storage cavity, and under the condition of inserting the unmanned aerial vehicle body in the first storage cavity, the inner walls of the cavities of the unmanned aerial vehicle body and the box body are in limit fit, and the wings are positioned in the limit grooves.

Further, the limiting groove comprises a straight groove section, an arc groove section and an opening section which are sequentially communicated, the opening section, the arc groove section and the straight groove section are sequentially arranged along the insertion direction of the unmanned aerial vehicle body, the straight groove section is used for accommodating the wing which rotates to the folding position, and in the process that the fuselage is inserted into the first accommodating cavity, the opening sections are abutted with the corresponding wings and drive the corresponding wings to rotate from the unfolding position to the folding position through the arc groove sections.

Further, accomodate the portion and still include the lid, box and lid detachably connect, and the lid has the second accomodates the chamber and along a plurality of spacing archs of the circumference distribution in chamber are accomodate to the second, under the circumstances that lid and box are connected, a plurality of spacing protruding one-to-one sets up in a plurality of spacing inslot, box and lid butt, and unmanned aerial vehicle body is accomodate to first accomodate chamber, second accomodate the chamber.

Further, the housing portion includes a case body having a first housing cavity, and the unmanned aerial vehicle body further includes a chassis structure provided on a bottom wall of the body, and the chassis structure is located outside the case body under the condition that the body is inserted into the first housing cavity.

By applying the technical scheme of the utility model, the unmanned aerial vehicle comprises: a storage section; the unmanned aerial vehicle body comprises a fuselage, a plurality of wings and a plurality of elastic components, wherein the plurality of elastic components are connected with the plurality of wings in a one-to-one correspondence manner, the plurality of wings are distributed around the circumference of the fuselage and are hinged with the fuselage, the fuselage and the plurality of wings are inserted in the containing part in a pluggable manner, and the wings have folding positions and unfolding positions relative to the fuselage; in the process of inserting the fuselage into the accommodating part, the accommodating part is abutted with the plurality of wings and drives the plurality of wings to rotate from the unfolding position to the folding position; in the process that the fuselage is pulled out from the storage part, a plurality of elastic components respectively drive corresponding wings to rotate from a folding position to an unfolding position. Adopt this scheme, under unmanned aerial vehicle body with the cooperation of accomodating the portion, can accomplish the folding of unmanned aerial vehicle body and accomodate the operation through pushing down the action, a plurality of wings rotate to folding position from the expansion position simultaneously in pushing down the in-process, under the cooperation of a plurality of wings and a plurality of elastic component, can accomplish the operation of taking out and deploying unmanned aerial vehicle body through carrying the pulling action, a plurality of wings rotate to expansion position from folding position simultaneously in carrying the pulling process. The folding and unfolding of the plurality of wings can be achieved in the process of storage and deployment of the unmanned aerial vehicle body, storage and deployment efficiency of the unmanned aerial vehicle body is improved, meanwhile, the plurality of wings rotate simultaneously, the situation that storage or deployment of the unmanned aerial vehicle body is carried out after the plurality of wings are required to be folded or unfolded respectively in the prior art is avoided, storage and deployment operation of the unmanned aerial vehicle body is simplified, and storage and deployment efficiency of the unmanned aerial vehicle body is further improved.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model. In the drawings:

fig. 1 shows an explosion schematic of a drone provided by an embodiment of the present utility model;

FIG. 2 illustrates a cross-sectional view of deployment and stowage of the drone of FIG. 1;

fig. 3 shows a deployment flow diagram of the drone of fig. 1.

Wherein the above figures include the following reference numerals:

10. a storage section; 11. a case; 111. a first receiving chamber; 112. a limit groove; 1121. a straight trough section; 1122. an arcuate slot section; 1123. an open section; 12. a cover body; 121. a limit protrusion; 20. an unmanned aerial vehicle body; 21. a body; 211. a receiving groove; 22. a wing; 221. a horn; 222. a blade assembly; 2221. a motor; 2222. a blade; 223. a stop block; 23. an elastic component; 231. a slide block; 232. a support rod; 233. an elastic member; 24. and (3) a chassis structure.

Detailed Description

The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the utility model, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

As shown in fig. 1 to 3, an embodiment of the present utility model provides a unmanned aerial vehicle, including: a storage section 10; the unmanned aerial vehicle body 20, unmanned aerial vehicle body 20 includes fuselage 21, a plurality of wings 22 and a plurality of elastic components 23 that connect with a plurality of wings 22 one-to-one, a plurality of wings 22 are distributed around the circumference of fuselage 21 and articulated with fuselage 21, fuselage 21 and a plurality of wings 22 are all inserted in the containing part 10 in a pluggable manner, and wings 22 have folding position and unfolding position relative to fuselage 21; during insertion of the fuselage 21 into the receiving portion 10, the receiving portion 10 and the plurality of wings 22 abut and drive the plurality of wings 22 to rotate from the extended position to the folded position; during the process of pulling out the body 21 from the storage part 10, the plurality of elastic assemblies 23 respectively drive the corresponding wings 22 to rotate from the folded position to the unfolded position.

In this embodiment, under the cooperation of the unmanned aerial vehicle body 20 and the accommodating portion 10, the operation of folding and accommodating the unmanned aerial vehicle body 20 can be completed through the pressing action, the plurality of wings 22 simultaneously rotate from the unfolding position to the folding position in the pressing process, under the cooperation of the plurality of wings 22 and the plurality of elastic components 23, the operation of taking out and deploying the unmanned aerial vehicle body 20 can be completed through the lifting action, and the plurality of wings 22 simultaneously rotate from the folding position to the unfolding position in the lifting process. The setting like this can realize folding and expanding to a plurality of wings 22 at the in-process of accomodating and deploying unmanned aerial vehicle body 20, has improved accomodating and deploying efficiency to unmanned aerial vehicle body 20, simultaneously, a plurality of wings 22 rotate simultaneously, has avoided among the prior art to need fold respectively or to expand the back to a plurality of wings 22 again to accomodate or the circumstances of deploying unmanned aerial vehicle body 20, has simplified accomodating and deploying operation to unmanned aerial vehicle body 20, has further improved accomodating and deploying efficiency to unmanned aerial vehicle body 20. Specifically, the unmanned aerial vehicle body 20 is in a deployed state when the plurality of wings 22 are in the deployed position, and the unmanned aerial vehicle body 20 is in a stowed state when the plurality of wings 22 are in the folded position.

As shown in fig. 2 and 3, the rotation direction of the wing 22 is the same as the insertion and extraction direction of the fuselage 21, and when the unmanned aerial vehicle body 20 is inserted into the accommodating portion 10, the plurality of wings 22 are all in the folded position, and the extending direction of the plurality of wings 22 is parallel to or has an included angle with the insertion and extraction direction of the fuselage 21; when the unmanned aerial vehicle body 20 and the storage part 10 are separated, the fuselage 21 and the plurality of wings 22 are spaced from the storage part 10, the plurality of wings 22 are in the unfolded position, the plurality of wings 22 are located on the same plane, and the extending direction of the plurality of wings 22 is perpendicular to the inserting and extracting direction of the fuselage 21. The extending direction of the wings 22 when in the folded position is parallel to the inserting and pulling direction of the body 21 or has an included angle, so that the overall size of the unmanned aerial vehicle body 20 required for accommodating is reduced, the overall size of the unmanned aerial vehicle is reduced, and the unmanned aerial vehicle is convenient to carry. The extending direction of the wings 22 when being in the unfolding position is positioned on the same plane, and the extending direction of the wings 22 is vertical to the inserting and pulling direction of the fuselage 21, so that the stability of the unmanned aerial vehicle body 20 during taking off is ensured, the unstable flying condition of the unmanned aerial vehicle body 20 due to the deviation of part of the wings 22 (namely, the included angle exists between the extending direction of the wings 22 and the inserting and pulling direction of the fuselage 21) during taking off is avoided, and the reliability of the unmanned aerial vehicle body 20 is ensured.

As shown in fig. 1 to 3, the outer peripheral surface of the body 21 is provided with a plurality of accommodating grooves 211 corresponding to the plurality of elastic components 23 one by one, the extending directions of the accommodating grooves 211 are parallel to the inserting and pulling directions of the body 21, the elastic components 23 comprise a sliding block 231, a supporting rod 232 and an elastic piece 233, the sliding block 231 and the elastic piece 233 are arranged in the accommodating grooves 211, the sliding block 231 is movably arranged and is abutted to the elastic piece 233, one end of the supporting rod 232 is fixedly connected with the sliding block 231, and the other end of the supporting rod 232 is hinged to the wing 22.

In the present embodiment, during the process of inserting the body 21 into the accommodating portion 10, the accommodating portion 10 abuts against the plurality of wings 22 and drives the plurality of wings 22 to rotate from the extended position to the folded position, and during this process, the support rods 232 move along with the rotation of the wings 22 and drive the sliding blocks 231 to move in the direction of the compression elastic members 233; in the process of pulling out the body 21 from the accommodating part 10, the plurality of elastic components 23 respectively drive the corresponding wings 22 to rotate from the folded position to the unfolded position, in the process, the elastic pieces 233 stretch and drive the sliding blocks 231 to move reversely, and the sliding blocks 231 drive the supporting rods 232 to move and realize the rotation driving of the wings 22. The automatic unfolding of the wings 22 is achieved through the cooperation of the sliding blocks 231, the supporting rods 232 and the elastic pieces 233, the situation that the wings 22 still need to be manually unfolded after the unmanned aerial vehicle body 20 is taken out in the prior art is avoided, and the deployment efficiency of the unmanned aerial vehicle body 20 is improved. Further, the accommodation and guide of the slider 231 is achieved by providing the accommodation groove 211, and the reliability of the movement of the slider 231 is ensured.

As shown in fig. 1, the accommodating groove 211 includes a first groove body and a second groove body which are mutually communicated, the width of the second groove body is larger than that of the first groove body, the first groove body is used for accommodating the supporting rod 232, the sliding block 231 and the elastic piece 233 are arranged in the second groove body, and the sliding block 231 is movably arranged and is abutted against the top wall of the second groove body so as to limit the rotation range of the wing 22. The setting like this, realize accomodating bracing piece 232 through first cell body and second cell body, avoid wing 22 at folding in-process, the interference appears in the outer wall of bracing piece 232 and fuselage 21 and lead to the circumstances that the folding angle of wing 22 is limited, guarantee the reliability of wing 22 folding. Further, the top wall of the sliding block 231 and the top wall of the second groove body are matched, the sliding block 231 is prevented from rotating to the unfolding position from the folding position in the wing 22, the sliding block 231 is prevented from excessively rotating under the action of the elastic piece 233, the wing 22 is excessively rotated, the unmanned aerial vehicle body 20 cannot take off, and the reliability of the unmanned aerial vehicle body 20 is guaranteed.

Specifically, in the case of inserting the unmanned aerial vehicle body 20 in the present embodiment into the housing 10, an angle is formed between the extending direction of the wing 22 and the inserting and extracting direction of the fuselage 21, and an angle is formed between the extending direction of the support bar 232 and the inserting and extracting direction of the fuselage 21.

Optionally, a telescopic guide rod is arranged in the second groove, the elastic piece 233 is a spring, the spring is sleeved on the guide rod, the situation that the spring is separated from the second groove is avoided, and the sliding block 231 is in butt joint with the spring and the guide rod and is movably arranged.

As shown in fig. 1 to 3, the wing 22 includes a horn 221 and a blade assembly 222, one ends of the horn 221 are respectively disposed at the same side of the extending direction of the plurality of receiving grooves 211 and hinged to the body 21, and the blade assembly 222 includes a motor 2221 and a plurality of blades 2222, the motor 2221 is disposed at the other end of the horn 221 and is in driving connection with the plurality of blades 2222 to drive the plurality of blades 2222 to rotate.

In this embodiment, one end of the supporting rod 232 is hinged to the arm 221, and under the condition that the wings 22 are in the unfolded positions, the motors 2221 are driven simultaneously, so that the blades 2222 rotate simultaneously, and a stable start of the unmanned aerial vehicle body 20 is realized. Specifically, as shown in fig. 2 and 3, each set of blade assemblies 222 includes two blades 2222, and as wing 22 rotates from the extended position to the folded position, both blades 2222 sag under their own weight and are folded for storage.

Specifically, the wing 22 includes a plurality of stop blocks 223, the stop blocks 223 are disposed on a side of the horn 221 away from the accommodating groove 211 along the extending direction of the accommodating groove 211, and the stop blocks 223 and the horn 221 are in stop fit to limit the rotation range of the horn 221. The setting like this, realize the backstop to horn 221 through backstop piece 223, avoid slider 231 at wing 22 from folding position rotation to the in-process of expansion position, the wing 22 rotates the condition that excessive lead to unmanned aerial vehicle body 20 unable take off, guarantees unmanned aerial vehicle body 20's reliability.

As shown in fig. 1 to 3, the housing portion 10 includes a housing 11, the housing 11 has a first housing cavity 111 and a plurality of limit grooves 112 distributed along a circumferential direction of the first housing cavity 111, the unmanned aerial vehicle body 20 is pluggable and inserted into the first housing cavity 111, in a process of inserting the fuselage 21 into the first housing cavity 111, openings of the plurality of limit grooves 112 are respectively abutted against corresponding wings 22 and drive the plurality of wings 22 to rotate from an unfolding position to a folding position, and in a case of inserting the unmanned aerial vehicle body 20 into the first housing cavity 111, the fuselage 21 and an inner wall of the cavity of the housing 11 are in limit fit, and the plurality of wings 22 are located in the plurality of limit grooves 112. The arrangement realizes limit and guide of the wing 22, reserves a storage position for the wing 22 rotating to a folding position, ensures the reliability of limit fit between the wing 22 and the limit groove 112 while ensuring the reliability of limit fit between the unmanned aerial vehicle body 20 and the inner wall of the first storage cavity 111 after being inserted into the first storage cavity 111.

As shown in fig. 1, the limiting groove 112 includes a straight groove section 1121, an arc groove section 1122 and an opening section 1123 which are sequentially communicated, the opening section 1123, the arc groove section 1122 and the straight groove section 1121 are sequentially arranged along the insertion direction of the unmanned aerial vehicle body 20, the straight groove section 1121 is used for accommodating the wing 22 which rotates to the folding position, and in the process that the fuselage 21 is inserted into the first accommodating cavity 111, the opening sections 1123 and the corresponding wings 22 are abutted and drive the corresponding wings 22 to rotate from the unfolding position to the folding position through the arc groove sections 1122. The setting like this, realize the accomodating of wing 22 that is located the folding position through straight slot section 1121, realize the butt to wing 22 through setting up opening section 1123, the staff of being convenient for inserts the prepositioning of accomodating portion 10 to unmanned aerial vehicle body 20, realize the rotation direction to wing 22 through arc slot section 1122, avoided wing 22 when straight slot section 1121 directly rotates, the corner position of straight slot section 1121 can cause the damage to wing 22, or rotate unsmooth, easily lead to the circumstances that wing 22 damaged, guarantee wing 22 pivoted reliability.

Specifically, the accommodating portion 10 further includes a cover body 12, the case body 11 and the cover body 12 are detachably connected, the cover body 12 has a second accommodating cavity and a plurality of spacing protrusions 121 distributed along the circumference of the second accommodating cavity, under the condition that the cover body 12 and the case body 11 are connected, the plurality of spacing protrusions 121 are arranged in the plurality of spacing grooves 112 in one-to-one correspondence, the case body 11 and the cover body 12 are abutted, and the unmanned aerial vehicle body 20 is accommodated in the first accommodating cavity 111 and the second accommodating cavity. This arrangement facilitates the connection of the case 11 and the cover 12, wherein the plurality of stopper protrusions 121 are disposed in the opening sections 1123 of the plurality of stopper grooves 112 in one-to-one correspondence in the case where the case 11 and the cover 12 are connected.

Further, the housing portion 10 includes a case 11, the case 11 has a first housing cavity 111, the unmanned aerial vehicle body 20 further includes a chassis structure 24 provided on a bottom wall of the body 21, and the chassis structure 24 is located outside the case 11 with the body 21 inserted into the first housing cavity 111. In this way, the operator can hold the chassis structure 24 to realize the lifting or pressing operation of the body 21, so as to improve the lifting or pressing efficiency of the unmanned aerial vehicle body 20. Specifically, as shown in fig. 2 and 3, in the case where the fuselage 21 is inserted into the first accommodating cavity 111, that is, in the case where the unmanned aerial vehicle body 20 is accommodated in the case 11 (where the plurality of wings 22 are located at the folded positions), the chassis structure 24 protrudes out of the first accommodating cavity 111, and a worker can directly hold the chassis structure 24 and pull the unmanned aerial vehicle body 20 out of the case 11 as a whole, and in the same way, in the process of accommodating the unmanned aerial vehicle body 20 in the deployed state (where the plurality of wings 22 are located at the unfolded positions) into the case 11, the worker can directly hold the chassis structure 24 to complete the operation of inserting the unmanned aerial vehicle body 20 into the first accommodating cavity 111 of the case 11. Specifically, the second receiving cavity is configured to receive the chassis structure 24 when the cover 12 and the case 11 are connected.

As shown in fig. 3, the procedure of deployment of the unmanned aerial vehicle provided in this embodiment is as follows:

1. opening the cover 12;

2. the unmanned aerial vehicle body 20 is gradually separated from the box 11 by lifting the underframe structure 24;

3. in the lifting and separating process, the elastic piece 233 gradually expands and pushes the sliding block 231 to move, and the sliding block 231 drives the supporting rod 232 to move so as to drive the wing 22 to rotate. As wing 22 slides into arcuate slot 1122, wing 22 begins to gradually expand along the arcuate limit of arcuate slot 1122 under the tension of resilient member 233. When the unmanned aerial vehicle body 20 is completely separated from the box 11, the wing 22 rotates to the unfolding position, that is, the extending direction of the wing 22 is unfolded to a state that the included angle between the extending direction and the inserting and pulling direction of the fuselage 21 is 90 degrees;

4. the unmanned aerial vehicle body 20 is lifted to be completely separated from the box 11 and then turned over for 180 degrees, so that the underframe structure 24 is downward and placed on the flat ground, and the deployment of the unmanned aerial vehicle is completed.

Similarly, the reverse operation of the deployment flow in fig. 3 is the storage flow of the unmanned aerial vehicle provided in this embodiment, and the flow during storage of the unmanned aerial vehicle is as follows:

1. after the unmanned aerial vehicle body 20 is powered off in a landing way, the unmanned aerial vehicle body 20 is turned over for 180 degrees by holding the underframe structure 24;

2. aligning the opened wings 22 with the corresponding opening sections 1123 of the case 11, and applying pressure vertically downward; the wing 22 starts to gradually fold inwards under the action of the extrusion force, so that the support rods 232 are driven to fold inwards and the sliding blocks 231 are driven to move upwards, and meanwhile the elastic pieces 233 are compressed; at this time, the multiple groups of blades 2222 gradually rotate around the axis of the motor 2221 and fold together under the action of gravity;

3. when the drone body 20 is fully pressed into the box 11, the wings 22 complete the adduction fold. While the folded blade assembly 222 also slides into and is secured within the straight slot segment 1121 with the assistance of the arcuate slot segment 1122. At this time, the elastic member 233 is in a compressed state under the pressure of the slider 231 and the support rod 232, and the wing 22 maintains the external tension under the action of the compression elastic member 233, so that the deployment of the next unmanned aerial vehicle body 20 after being taken out is ready.

4. The cover 12 is covered to complete the storage of the unmanned aerial vehicle body 20.

The above description is only of the preferred embodiments of the present utility model and is not intended to limit the present utility model, but various modifications and variations can be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.

Claims (10)

1. An unmanned aerial vehicle, comprising:

a storage unit (10);

the unmanned aerial vehicle body (20), unmanned aerial vehicle body (20) includes fuselage (21), a plurality of wing (22) and a plurality of elastic component (23) that connect with a plurality of wing (22) one-to-one, a plurality of wing (22) around the circumference of fuselage (21) distributes and with fuselage (21) articulated, fuselage (21) and a plurality of wing (22) are all pluggable and insert and establish in holding portion (10), wing (22) have folding position and expansion position relative to fuselage (21); during insertion of the fuselage (21) into the receiving portion (10), the receiving portion (10) and the plurality of wings (22) abut and urge the plurality of wings (22) to rotate from the extended position to the folded position; during the process of the fuselage (21) being pulled out of the containing part (10), a plurality of elastic assemblies (23) respectively drive the corresponding wings (22) to rotate from the folding position to the unfolding position.

2. The unmanned aerial vehicle according to claim 1, wherein the direction of rotation of the wing (22) is the same as the direction of insertion and extraction of the fuselage (21),

when the unmanned aerial vehicle body (20) is inserted into the accommodating part (10), the wings (22) are all positioned at the folding position, and the extending direction of the wings (22) is parallel to or has an included angle with the inserting and pulling direction of the body (21);

under the condition that the unmanned aerial vehicle body (20) is separated from the accommodating part (10), the fuselage (21) and the wings (22) are spaced from the accommodating part (10), the wings (22) are in unfolding positions, the wings (22) are located on the same plane, and the extending direction of the wings (22) is perpendicular to the inserting and pulling direction of the fuselage (21).

3. The unmanned aerial vehicle according to claim 1, wherein the outer peripheral surface of the fuselage (21) is provided with a plurality of accommodating grooves (211) corresponding to the elastic components (23) one by one, the extending directions of the accommodating grooves (211) are parallel to the inserting and pulling directions of the fuselage (21), the elastic components (23) comprise sliding blocks (231), supporting rods (232) and elastic pieces (233), the sliding blocks (231) and the elastic pieces (233) are arranged in the accommodating grooves (211), the sliding blocks (231) are movably arranged and are abutted to the elastic pieces (233), one ends of the supporting rods (232) are fixedly connected with the sliding blocks (231), and the other ends of the supporting rods (232) are hinged to the wings (22).

4. A drone according to claim 3, wherein the receiving slot (211) comprises a first slot body and a second slot body which are in communication with each other, the second slot body having a width greater than the width of the first slot body, the first slot body being adapted to receive the support bar (232), the slider (231) and the elastic member (233) being arranged in the second slot body, the slider (231) being movably arranged and abutting against a top wall of the second slot body to limit the rotation range of the wing (22).

5. A unmanned aerial vehicle according to claim 3, wherein the wing (22) comprises a horn (221) and a blade assembly (222), one ends of the horns (221) are respectively arranged on the same side of the extending direction of the accommodating grooves (211) and hinged with the fuselage (21), the blade assembly (222) comprises a motor (2221) and a plurality of blades (2222), and the motor (2221) is arranged at the other end of the horn (221) and is in driving connection with the blades (2222) so as to drive the blades (2222) to rotate.

6. The unmanned aerial vehicle according to claim 5, wherein the wing (22) comprises a plurality of stop blocks (223), the stop blocks (223) are arranged on one side of the horn (221) away from the accommodating groove (211) along the extending direction of the accommodating groove (211), and the stop blocks (223) and the horn (221) are in stop fit to limit the rotation range of the horn (221).

7. The unmanned aerial vehicle according to claim 1, wherein the housing part (10) comprises a housing body (11), the housing body (11) is provided with a first housing cavity (111) and a plurality of limit grooves (112) distributed along the circumferential direction of the first housing cavity (111), the unmanned aerial vehicle body (20) is pluggable and inserted into the first housing cavity (111), in the process of inserting the fuselage (21) into the first housing cavity (111), the openings of the limit grooves (112) are respectively abutted with the corresponding wings (22) and drive the wings (22) to rotate from the unfolding position to the folding position, and under the condition that the unmanned aerial vehicle body (20) is inserted into the first housing cavity (111), the fuselage (21) and the inner walls of the housing body (11) are in limit fit, and the wings (22) are located in the limit grooves (112).

8. The unmanned aerial vehicle according to claim 7, wherein the limiting groove (112) comprises a straight groove section (1121), an arc groove section (1122) and an opening section (1123) which are sequentially communicated, the opening section (1123), the arc groove section (1122) and the straight groove section (1121) are sequentially arranged along the insertion direction of the unmanned aerial vehicle body (20), the straight groove section (1121) is used for accommodating the wing (22) which rotates to the folding position, and in the process of inserting the fuselage (21) into the first accommodating cavity (111), a plurality of the opening sections (1123) and the corresponding wings (22) are abutted and are driven to rotate from the unfolding position to the folding position through a plurality of the arc groove sections (1122).

9. The unmanned aerial vehicle according to claim 7, wherein the housing part (10) further comprises a cover body (12), the case body (11) is detachably connected with the cover body (12), the cover body (12) is provided with a second housing cavity and a plurality of limiting protrusions (121) distributed along the circumferential direction of the second housing cavity, the plurality of limiting protrusions (121) are arranged in the plurality of limiting grooves (112) in a one-to-one correspondence manner under the condition that the cover body (12) is connected with the case body (11), the case body (11) is abutted with the cover body (12), and the first housing cavity (111) and the second housing cavity house the unmanned aerial vehicle body (20).

10. The unmanned aerial vehicle according to claim 1, wherein the receiving portion (10) comprises a box (11), the box (11) having a first receiving cavity (111), the unmanned aerial vehicle body (20) further comprising a chassis structure (24) provided on a bottom wall of the fuselage (21), the chassis structure (24) being located outside the box (11) with the fuselage (21) inserted into the first receiving cavity (111).